RamjetH2:

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   Ramjet model including aerodynamic losses. The default fuel is H2.
   Computes the thrust and exhaust velocity including aerodynamic losses.

   Inputs u and h must have the same lengths. This function calls the 
   standard atmosphere model

   Type

   RamjetH2

   for a demo. The demo varies the altitude from 10 to 40 km and the Mach
   number from 1 to 4.5.

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   Form:
   [t, tSFC, uE, f, M, iSp, thR] = RamjetH2( u, h, d )
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   ------
   Inputs
   ------
   u           (1,:)  Velocity (m/s)
   h           (1,:)  Altitude (m)
   d           (1,1)  Data structure
                      .gamma    (1,1) Airflow ratio of specific heats
                      .etaB     (1,1) Combustion efficiency
                      .qR       (1,1) Joules/kg for the fuel  (default H2)
                      .t04      (1,1) Combustor temperature
                      .cP       (1,1) Air specific heat
                      .pEOverPA (1,1) Ratio of exit pressure to atmospheric pressure
                      .aI       (1,1) Inlet area
                      .rD       (1,1) Diffuser pressure ratio
                      .rC       (1,1) Combustor pressure ratio
                      .rN       (1,1) Nozzle pressure ratio
                      .aE       (1,1) Exit area

   -------
   Outputs
   -------
   t           (1,:)  Thrust (N)
   tSFC        (1,:)  Thrust specific fuel consumption
   uE          (1,:)  Exhaust velocity (m/s)
   f           (1,:)  Fuel air ratio
   m           (1,:)  Mach number
   iSp         (1,:)  Specific impulse (sec)
   thR         (1,:)  Thrust to mass flow ratio

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   Reference: Hill, P.G. and Peterson, C. R., "The Mechanics and
              Thermodynamics of Propulsion," Addison-Wesley, Reading, MA, 1970, pp.
              154-157.
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Children:

Common: General/StdAtm
Common: Graphics/Plot2D
Propulsion: Chemical/QRHydrogen